US3815850A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Crab angle reference signal development for limited forward slip landing maneuver
Assignee: Collins Radio Co
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Filing: 1972-11-24
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Granted: 1974-06-11
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Expires: 1992-11-24
Abstract
Abstract A signal processing apparatus for developing a yaw command signal as might be advantageously employed in effecting decrab prior to touchdown. The signal is formulated from utlizing course datum prior to decrab to reference an integrator to which yaw rate is applied during decrab. A limiter processes the yaw command signal to establish a maximum permissible decrab maneuver.
Inventors
- 👤 R Tribuno
- 👤 J Foster
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 23:05
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/02; G05D1/0202; G05D1/0204; G05D1/04; G05D1/06; G05D1/0607; G05D1/0653; G05D1/0676
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
217 words
In an automatic control system for aircraft, control means for developing a yaw steering command signal to effect a decrab maneuver of said aircraft upon a predetermined aircraft altitude being experienced, comprising, signal integrating means, a source of course datum signal proportional to the discrepancy between experienced aircraft heading and a preselected heading, a yaw rate sensor producing a signal proportional to angular velocity about the yaw axis of said aircraft, means operative only at aircraft altitudes above said predetermined altitude to apply said course datum signal as input to said signal integrating means to produce an output signal from said integrating means proportional to the average course datum signal applied thereto, means responsive only to aircraft altitudes equal to and less than said predetermined altitude to apply said yaw rate sensor output signal as input to said signal integrating means, output signal mixing means receiving said yaw rate signal and the output signal from said signal integrating means as respective inputs thereto, means selectively responsive to aircraft altitudes equal to and less than said predetermined altitude to apply the output of said output signal mixing means to an output terminal as a yaw command signal, and aircraft yaw steering means responsive to the said yaw command output signal to effect a decrab maneuver of said aircraft.
Claim 2
Dependent Claim
217 words
In an automatic control system for aircraft, control means for developing a yaw steering command signal to effect a decrab maneuver of said aircraft upon a predetermined aircraft altitude being experienced, comprising, signal integrating means, a source of course datum signal proportional to the discrepancy between experienced aircraft heading and a preselected heading, a yaw rate sensor producing a signal proportional to angular velocity about the yaw axis of said aircraft, means operative only at aircraft altitudes above said predetermined altitude to apply said course datum signal as input to said signal integrating means to produce an output signal from said integrating means proportional to the average course datum signal applied thereto, means responsive only to aircraft altitudes equal to and less than said predetermined altitude to apply said yaw rate sensor output signal as input to said signal integrating means, output signal mixing means receiving said yaw rate signal and the output signal from said signal integrating means as respective inputs thereto, means selectively responsive to aircraft altitudes equal to and less than said predetermined altitude to apply the output of said output signal mixing means to an output terminal as a yaw command signal, and aircraft yaw steering means responsive to the said yaw command output signal to effect a decrab maneuver of said aircraft.
Claim 3
Dependent Claim
128 words
A control system as defined in claim 1 wherein said signal integrating means comprises signal combining means, said course datum signal being applied as a first input to said signal combining means, a signal integrator selectively receiving the output of said signal combining means as input thereto for aircraft altitudes in excess of said predetermined altitude, the output of said signal integrator being applied in a subtractive sense as a second input to said signal combining means, means for applying said yaw rate sensor output signal as input to said signal integrator in lieu of the output of said signal combining means for aircraft altitudes equal to and less than said predetermined altitude, and the output of said signal integrator comprising the output from said signal integrating means.
Claim 4
Dependent Claim
42 words
A control system as defined in claim 2 further comprising signal limiting means receiving the output of said signal integrating means and limiting either sense input signal thereto to a predetermined maximum signal amplitude as applied to said output signal mixing means.
Claim 5
Dependent Claim
123 words
A control system as defined in claim 3 wherein said signal limiting means comprises means for developing and storing a signal proportional to the average value of the output of said signal integrating means during aircraft altitudes in excess of said predetermined altitude, dead-zone signal translating means receiving the output of said means for developing and storing as an input thereto and providing a unity gain output signal proportional to only those input signals having magnitudes in excess of a predetermined level, further signal mixing means receiving the outputs of said signal integrating means and said dead-zone signal translating means as respective mutually subtractive inputs thereto, and the output of said further signal mixing means being applied to said output signal mixing means.
Claim 6
Dependent Claim
98 words
A control system as defined in claim 4 wherein said means for developing and storing comprises a further signal combining means receiving the output of said signal integrating means as a first input thereto, a further signal integrator to which the output of said further signal combining means is selectively applied for aircraft altitudes in excess of said predetermined altitude, the output of said further signal integrating means being applied as a subtractive second input to said further signal integrator, and the output of said further signal integrator being applied as input to said dead-zone signal translating means.
Claim 7
Dependent Claim
95 words
A control system as defined in claim 5 wherein said aircraft control system comprises a roll steering command signal computing means, and cross feed signal development means for sElectively applying to said roll steering command computing means a cross feed signal with sensing like that of the output of said means for developing and storing and a magnitude like that of the output of said means for developing and storing and not exceeding said predetermined limit magnitude, said cross feed signal being selectively applied at a time corresponding to said predetermined aircraft altitude being experienced.
Claim 8
Dependent Claim
58 words
A control system as defined in claim 6 wherein said cross feed signal development means comprises means for subtracting the output of said dead-zone signal translating means from the input signal thereto, and further comprising bandpass filter means through which the output of said means for subtracting is selectively applied to said roll steering command signal computing means.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-06-10 | 1977-12-10 | 1978-06-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-06-10 | 1981-12-10 | 1982-06-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-06-10 | 1985-12-10 | 1986-06-11 | $7700.00 | Window Closed / Lapsed |